RU165003U1 - DEVICE FOR STABILIZING A FLAME IN AN AFTER CHAMBER OF A TURBO-REACTIVE ENGINE - Google Patents

Abstract

A device for stabilizing the flame in the afterburner of a turbojet engine, comprising a housing in which there is a turbine cowl with a system of radially arranged nozzles, an air sampling nozzle, a fuel nozzle and a gas jet generating device that is installed inside the turbine jet cowl and connected to a sampling nozzle, characterized in that The device for generating gas jets is made in the form of a constant-volume spool-type combustion chamber, which is connected to nozzles, and the nozzle is installed inside Air sampling tube.

Description

The utility model relates to gas turbine engines, namely to the design of afterburners and devices for stabilizing the flame in the afterburner.

A device is known for stabilizing a flame in an afterburner of an aircraft-jet engine (description of the RF patent for invention No. 2208204, IPC F23R 3/22, publ. 07/10/2003).

In the device for flame stabilization, rotary radial V-shaped stabilizers are used, which are removed from the flow at the engine afterburning mode to reduce hydraulic losses in the FC.

The disadvantage of this device is the possibility of jamming of rotary mechanisms operating at high temperatures, as well as the complexity of the design and the additional mass of the drive mechanism.

Closest to the proposed one is a device for stabilizing a flame in a afterburner of a turbojet engine, comprising a housing in which a turbine cowling with a system of radially arranged nozzles is located, an air intake pipe, a fuel nozzle and a gas jet generating device that is installed inside the turbine jet cowling and connected to the pipe air selection (description of the patent of the Russian Federation for the invention No. 2403422, IPC F23R 3/18, publ. 10.11.2010).

Gas-dynamic stabilization of the flame in the afterburner is ensured by the use of a small-sized gas turbine engine located in the turbine cowl, a flame arrester and a system of radially arranged nozzles. The device allows to exclude hydraulic losses in afterburner modes. In this case, the disadvantages include the reduced combustion efficiency of the air-fuel mixture, as well as the increase in mass and a significant complication of the design.

The technical result, which the utility model is aimed at, is to increase the efficiency of ignition and combustion of the air-fuel mixture due to the impact of the pulsating flow of gas jets on it, while the gas jet generator is a combustion chamber with a constant volume of fuel combustion and a rotating spool.

An additional technical result is to simplify the design of the device through the use of a combustion chamber with a constant volume of fuel combustion due to the lack of a compressor and a turbine in comparison with the small gas turbine engine used in the prototype.

The technical result is achieved by the fact that in a device for stabilizing a flame in an afterburner of a turbojet engine comprising a housing in which a turbine cowling with a system of radially arranged nozzles is located, an air intake pipe, a fuel nozzle and a gas jet generating device that is installed inside the turbine cowling and connected with a sampling pipe, in contrast to the known one, the device for generating gas jets is made in the form of a spool-type combustion chamber of constant volume, which is connected Nena with nozzles and nozzle installed inside the air bleed pipe.

The utility model is illustrated by the drawings on which are shown:

FIG. 1 - the proposed device;

FIG. 2 - the proposed device with a spool-type combustion chamber of constant volume with a longitudinal axis of rotation;

FIG. 3 - the proposed device with a spool chamber of combustion of constant volume with a transverse axis of rotation.

A device for stabilizing a flame in an afterburner of a turbojet engine (Fig. 1) comprises a afterburner body 1 in which a turbine cowling 2 is located.

The device 3 for generating gas jets is made in the form of a spool-type combustion chamber of constant volume. The design of a spool-type combustion chamber of constant volume, for example, with a longitudinal axis of rotation, is presented in RF patent for invention No. 2440501, IPC F02C 5/02, publ. 01/20/2012 (Fig. 2), and with a transverse axis of rotation, is presented, for example, in the patent of the Russian Federation for invention No. 2196906, IPC F02C 5/02, publ. 01/20/2003 (Fig. 3).

The constant-volume spool-type combustion chamber is located in the turbine cowl 2 and is connected on one side to the air intake pipe 4 from the external or internal engine circuit (depending on the engine design), and, on the other hand, to a system of radially arranged nozzles 5.

Inside the nozzle 4 air sampling in front of the spool chamber of combustion of constant volume installed fuel nozzle 6.

A device for stabilizing the flame in the afterburner of a turbojet engine operates as follows.

During the operation of a turbojet engine, air from the external or internal circuit of the engine entering the air intake pipe 4 is mixed with the fuel supplied by the nozzle 6. The resulting air-fuel mixture enters the constant-volume combustion chamber 3. The air-fuel mixture ignites from the standby flame, and at the start - from a candle (not shown in the drawing), and burns in a closed volume with increasing pressure. Further, from the combustion chamber of constant volume, the exhaustion of combustion products takes place, then purging and filling with a fresh charge of the air-fuel mixture, and the filling-ignition-combustion-expiration-purge duty cycle is repeated. High-frequency gas jets flowing through radial nozzles 5 form a pulsating vortex zone of reverse currents in the afterburner to stabilize the flame and efficient combustion. The frequency of the gas jets is provided by the rotation frequency and the number of cavities of the spool of the combustion chamber of constant volume.

During the engine’s afterburning operation, the spool-type combustion chamber with a constant volume of fuel combustion is turned off — gas jets are not supplied — and this eliminates the hydraulic resistance of the afterburner.

In the proposed device for stabilizing the flame in the afterburner of a turbojet engine, the gas jet generator is a spool combustion chamber with a constant volume of fuel combustion, which due to the pulsating flow of gas jets provides increased ignition and combustion efficiency of the air-fuel mixture in the afterburner. The absence of hydraulic losses in the afterburner modes is ensured by the absence of combustion stabilizers and shutdown of the gas jet generator.

Claims (1)

A device for stabilizing the flame in the afterburner of a turbojet engine, comprising a housing in which there is a turbine cowl with a system of radially arranged nozzles, an air sampling nozzle, a fuel nozzle and a gas jet generating device that is installed inside the turbine jet cowl and connected to a sampling nozzle, characterized in that the device for generating gas jets is made in the form of a constant-volume spool-type combustion chamber, which is connected to nozzles, and the nozzle is installed inside Air sampling tube.

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